Tests on a 5-per-cent Biconvex Aerofoil in the Compressed-Air Tunnel

dc.contributor.author	D. H. Williams	en_US
dc.contributor.author	A. H. Bell	en_US
dc.date.accessioned	2014-10-21T15:54:07Z
dc.date.available	2014-10-21T15:54:07Z
dc.date.issued	1945	en_US
dc.identifier.other	ARC/R&M-2413	en_US
dc.identifier.uri	https://reports.aerade.cranfield.ac.uk/handle/1826.2/3555
dc.description.abstract	A symmetrical 5 per cent. biconvex aerofoil has been tested from R = 0.3 x 10(to power 6) to R = 7.5 x l0(to power 6). No scale effect was found on Cz. To show the effect of camber, comparative curves are given for circular-back aerofoils. Cz .... increases linearly with camber from 0.7 for the symmetrical wing to 1.18 for a wing with 6 per cent camber. The aerofoil was also tested with a 15 per cent. split flap.	en_US
dc.relation.ispartofseries	Aeronautical Research Council Reports & Memoranda	en_US
dc.title	Tests on a 5-per-cent Biconvex Aerofoil in the Compressed-Air Tunnel	en_US